Micromachined gyroscope including a guided mass system

ABSTRACT

A gyroscope is disclosed. The gyroscope comprises a substrate; and a guided mass system. The guided mass system comprises proof-mass and guiding arm. The proof-mass and the guiding arm are disposed in a plane parallel to the substrate. The proof-mass is coupled to the guiding arm. The guiding arm is also coupled to the substrate through a spring. The guiding arm allows motion of the proof-mass to a first direction in the plane. The guiding arm and the proof-mass rotate about a first sense axis. The first sense axis is in the plane and parallel to the first direction. The gyroscope includes an actuator for vibrating the proof-mass in the first direction. The gyroscope also includes a transducer for sensing motion of the proof-mass-normal to the plane in response to angular velocity about a first input axis that is in the plane and orthogonal to the first direction.

CROSS-REFERENCE TO RELATED APPLICATION

Under 35 U.S.C. 120, this application is a Continuation Application and claims priority to U.S. application Ser. No. 13/235,296, filed Sep. 16, 2011, entitled “MICROMACHINED GYROSCOPE INCLUDING A GUIDED MASS SYSTEM,” which is incorporated herein by reference in its entirety.

FIELD OF THE INVENTION

The present invention relates generally to angular velocity sensors and more particularly relates to angular velocity sensors that include guided mass systems.

BACKGROUND OF THE INVENTION

Sensing of angular velocity is frequently performed using vibratory rate gyroscopes. Vibratory rate gyroscopes broadly function by driving the sensor into a first motion and measuring a second motion of the sensor that is responsive to both the first motion and the angular velocity to be sensed.

Frequently, a mass, usually referred to as a proof mass, within the sensor is driven into oscillation by an actuator. Rotation of the sensor imparts a Coriolis force to the oscillating mass that is proportional to the angular velocity (or rotation rate), and depends on the orientation of the angular velocity vector with respect to the velocity vector of the proof mass. The Coriolis force, the angular velocity vector, and the proof-mass velocity vector are mutually orthogonal. For example, a proof-mass moving in an X-direction within a sensor rotating about a Y-axis experiences a Z directed Coriolis force. Similarly, a proof-mass moving in an X-direction within a sensor rotating about a Z-axis experiences a Y directed Coriolis force. Finally, a proof-mass moving in an X-direction within a sensor rotating about the X-axis experiences no Coriolis force. Coriolis forces imparted to the proof-mass are usually sensed indirectly by measuring motions within the sensor that are responsive to the Coriolis forces.

Conventional gyroscopes that sense angular velocity about an in-plane axis (i.e. X-axis or Y-axis) can be driven out-of-plane, and the Coriolis response is sensed in-plane or vice versa. Out-of-plane drive tends to be less efficient than in-plane drive, requires additional fabrication steps, and is limited by nonlinearities. For example, driving the proof-mass out-of-plane might require a large vertical gap or a cavity underneath the proof-mass to provide sufficient room for the proof-mass to oscillate. Forming a cavity under the proof-mass requires additional fabrication steps and increases cost. Typically electrostatic actuators of the parallel-plate type are used to drive the proof-mass out-of-plane. The actuators are formed between the proof-mass and the substrate. The electrostatic force depends on the gap between the proof-mass and the substrate. Because the proof-mass oscillates out-of-plane, the electrostatic force is nonlinear which tends to limit the device performance. Additionally, the electrostatic force is reduced because of the requirement to have large vertical gaps or a cavity under the proof-mass. Achieving large amplitude oscillation requires large force and that might require high-voltage actuation. Adding high-voltage actuation increases the fabrication cost and complexity of the integrated circuits.

Furthermore a conventional multi-axis gyroscope might use multiple structures that oscillate at independent frequencies to sense angular rates. Each structure requires a separate drive circuit to oscillate the respective proof-masses. Having more than one drive circuit increases cost and power consumption.

Accordingly, what is desired is to provide a system and method that overcomes the above issues. The present invention addresses such a need.

SUMMARY OF THE INVENTION

A gyroscope is disclosed. In one embodiment, the gyroscope comprises a substrate; and a guided mass system. The guided mass system comprises at least one proof-mass and at least one guiding arm. The at least one proof-mass and the at least one guiding arm are disposed in a plane parallel to the substrate. The at least one proof-mass is coupled to the at least one guiding arm.

The at least one guiding arm is also coupled to the substrate through at least one spring. The at least one guiding arm allows for motion of the at least one proof-mass, in a first direction in the plane. The at least one guiding arm and the at least one proof-mass rotate about a first sense axis. The first sense axis is in the plane and parallel to the first direction.

The gyroscope includes an actuator for vibrating the at least one proof-mass in the first direction. The gyroscope also includes a transducer for sensing motion of at least one proof-mass normal to the plane in response to angular velocity about a first input axis that is in the plane and orthogonal to the first direction.

A method and system in accordance with the present invention provides a mechanical structure that oscillates at one frequency and is capable of sensing angular rate about multiple axes. One drive motion requires only one drive circuit, which lowers cost and power. Other aspects and advantages of the present invention will become apparent from the following detailed description, taken in conjunction with the accompanying drawings, illustrating by way of example the principles of the invention.

BRIEF DESCRIPTION OF THE DRAWINGS

FIGS. 1A-1C illustrate an embodiment of a gyroscope comprising a guided mass system in accordance with the present invention.

FIG. 2 illustrates an embodiment of a gyroscope comprising a symmetric guided mass system in accordance with the present invention.

FIG. 3 illustrates an embodiment of a gyroscope comprising a balanced guided mass system in accordance with the present invention.

FIG. 4 illustrates an embodiment of a gyroscope comprising a stress relieved guided mass system in accordance with the present invention.

FIG. 5 illustrates a first embodiment of a dual-axis gyroscope comprising a guided mass system in accordance with the present invention.

FIG. 6 illustrates a second embodiment of a dual-axis gyroscope comprising a guided mass system in accordance with the present invention.

FIG. 7 illustrates a third embodiment of a dual-axis gyroscope comprising a guided mass system in accordance with the present invention.

FIG. 8 illustrates an embodiment of a tri-axis gyroscope comprising a guided mass system in accordance with the present invention.

FIG. 9 illustrates a first embodiment of a dual-axis gyroscope comprising a balanced guided mass system in accordance with the present invention.

FIG. 10 illustrates a second embodiment of a dual-axis gyroscope comprising a balanced guided mass system in accordance with the present invention.

FIG. 11 illustrates a first embodiment of a tri-axis gyroscope comprising a multiple guided mass system in accordance with the present invention.

FIGS. 12A-12E illustrate a second embodiment of a tri-axis gyroscope comprising a stress relieved multiple guided mass system in accordance with the present invention.

DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS

The present invention relates generally to angular velocity sensors and more particularly relates to in-plane angular velocity sensors that have at least one proof mass. The following description is presented to enable one of ordinary skill in the art to make and use the invention and is provided in the context of a patent application and its requirements. Various modifications to the preferred embodiment and the generic principles and features described herein will be readily apparent to those skilled in the art. Thus, the present invention is not intended to be limited to the embodiment shown but is to be accorded the widest scope consistent with the principles and features described herein.

A method and system in accordance with the present invention provides a guided mass system as part of a gyroscope that oscillates at one frequency and is capable of sensing angular rate about multiple axes. One drive motion requires only one drive circuit, which lowers cost and power. To describe the features of the present invention in more detail refer now to following description on conjunction with the accompanying Figures.

FIG. 1A illustrates an embodiment of a gyroscope comprising a guided mass system 100 in accordance with the present invention. The guided mass system 100 is disposed in an X-Y plane parallel to a substrate 101. A Z-direction is normal to the X-Y plane. The guided mass system 100 includes guiding arms 104 a and 104 b that are flexibly coupled via springs 108 a and 108 b to the substrate 101 via at least one anchoring point 106 a. The two guiding arms 104 a and 104 b are flexibly coupled to one roll proof-mass 102 a via springs 103 a and 103 b.

The roll proof-mass 102 a, guiding arms 104 a and 104 b, anchoring point 106 a, and springs 103 a, 103 b, 108 a, and 108 b form a planar four-bar linkage. Each spring 103 a, 103 b, 108 a, and 108 b is compliant in-plane about an axis in the Z-direction so that each guiding arm 104 a and 104 b can rotate in-plane while the proof-mass 102 a translates in an X-direction, as shown in FIG. 1B.

The springs 108 a and 108 b are compliant about a first roll-sense axis in the X-direction so that the guiding arms 104 a and 104 b can rotate out-of-plane. The springs 103 a and 103 b are stiff in the Z-direction, whereby out-of-plane rotation of the guiding arms 104 a and 104 b causes the roll proof-mass 102 a to move out-of-plane with the guiding arms 104 a and 104 b, as shown in FIG. 1C.

Electrostatic actuators, such as comb drives 109 a and 109 b, are connected to the roll proof-mass 102 a to drive the guided mass system 100. In this embodiment, two electrostatic actuators are utilized. However, one of ordinary skill in the art readily recognizes that one electrostatic actuator can be provided and the use of one electrostatic actuator would be within the spirit and scope of the present invention. In addition, although electrostatic actuators will be described throughout this specification as the actuators being used to drive the guided mass systems one of ordinary skill in the art recognizes that a variety of actuators could be utilized for this function and that use would be within the spirit and scope of the present invention. For example, the actuators could be piezoelectric, thermal or electromagnetic or the like.

The guided mass system 100 can be driven at a drive frequency by a single drive circuit coupled to the actuators 109 a and 109 b. The drive frequency can be a resonant frequency of the guided mass system 100. When the guided mass system 100 is driven, the guiding arms 104 a and 104 b rotate in-plane and the roll proof-mass 102 a translates in-plane in the X-direction, as shown in FIG. 1B. Angular velocity about a roll-input axis in the Y-direction that is in the plane of the substrate and orthogonal to the X-direction will cause a Coriolis force to act on the roll proof-mass 102 a in the Z-direction. The Coriolis force causes the guided mass system 100 to rotate out-of-plane about the first roll-sense axis. When the guided mass system 100 rotates out-of-plane, the guiding arms 104 a and 104 b and the roll proof-mass 102 a rotate out-of-plane about the first roll-sense axis, as shown in FIG. 1C. The amplitude of the rotation of the guided mass system 100 is proportional to the angular velocity about the roll-input axis. A transducer 112 a under the roll proof-mass 102 a is used to detect the rotation of the guided mass system 100 about the first roll-sense axis. This rotation provides a measure of the angular velocity about the roll-input axis. A variety of types of transducers could be utilized in the present invention. For example, the transducer 112 a could be capacitive, piezoelectric, or optical or the like and its use would be within the spirit and scope of the present invention.

FIG. 2 illustrates an embodiment of a gyroscope comprising a symmetric guided mass system 200 in accordance with the present invention. The symmetric guided mass system 200 includes similar elements and connections to that of the guided mass system 100 and those elements and connections have similar reference numbers. The symmetric guided mass system 200 includes an additional roll proof-mass 102 b coupled to guiding arms 104 a and 104 b via springs 103 c and 103 d. The guiding arms 104 a and 104 b, roll proof masses 102 a and 102 b, and coupling springs 103 a-d form a planar four-bar linkage. Additional electrostatic actuators 109 c and 109 d are connected to the additional roll proof-mass 102 b to drive the symmetric guided mass system 200.

The symmetric guided mass system 200 can be driven at a drive frequency by a single drive circuit coupled to the actuators 109 a-d. When the guided mass system 200 is driven, each of the guiding arms 104 a and 104 b rotates in-plane about different axes in the Z-direction and the roll proof masses 102 a and 102 b translate anti-phase along the X-direction. In the present specification, anti-phase means in opposing directions, and in-phase means in the same direction. Angular velocity about the roll-input axis will cause Coriolis forces to act on the roll proof-masses 102 a and 102 b anti-phase in the Z-direction. The Coriolis forces cause the guided mass system 200 to rotate out-of-plane about the first roll-sense axis. When the guided mass system 200 rotates out-of-plane, the guiding arms 104 a and 104 b rotate about the first roll-sense axis, and the roll proof-masses 102 a and 102 b are constrained to move anti-phase out-of-plane by the guiding arms 104 a and 104 b. Transducers 112 a and 112 b under the roll proof masses 102 a and 102 b respectively are used to detect the rotation of the guided mass system 200 about the first roll-sense axis. This rotation provides a measure of the angular velocity about the roll-input axis.

FIG. 3 illustrates an embodiment of a gyroscope comprising a balanced guided mass system 300 in accordance with the present invention. The balanced guided mass system 300 includes two symmetric guided mass systems 200 a and 200 b coupled together by a coupling spring 302 a. The two symmetric guided mass systems are arranged so that the roll proof-masses 102 a-d all move in the X-direction. The symmetric guided mass system 200 a rotates out-of-plane about a first roll-sense axis. The symmetric guided mass system 200 b rotates out-of-plane about a second roll-sense axis in-plane and parallel to the first roll-sense axis. The coupling spring 302 a is connected to roll proof-masses 102 b and 102 c. The coupling spring 302 a is stiff in the X-direction such that roll proof-masses 102 b and 102 c move together in the X-direction. In this way the two symmetric guided mass systems 200 a and 200 b are driven together at a drive frequency by a single drive circuit coupled to the actuators 109 a-h. The coupling spring 302 a is torsionally compliant about an axis in the X-direction so that the symmetric guided mass systems 200 a and 200 b can rotate anti-phase out-of-plane about the first and second roll-sense axes. The coupling spring 302 a is stiff in the Z-direction which prevents the symmetric guided mass systems 200 a and 200 b from rotating in-phase out-of-plane.

The balanced guided mass system 300 allows for a gyroscope that is sensitive to angular velocity about the roll-input axis and rejects angular acceleration about an X-input axis in the X-direction. Angular velocity about the roll-input axis causes Coriolis forces to act on the roll proof-masses 102 a-d in the positive and negative Z-direction. The Coriolis forces cause the symmetric guided mass systems 200 a and 200 b to rotate anti-phase out-of-plane about the first and second roll-sense axes. Transducers 112 a-c under the roll proof masses 102 a-d are used to detect the rotations of the symmetric guided mass systems 200 a and 200 b about the first and second roll-sense axes.

Externally applied angular acceleration about the X-input axis will generate in-phase inertial torques on the symmetric guided mass systems 200 a and 200 b. However, the symmetric guided mass systems do not rotate because coupling spring 302 a prevents in-phase rotation about the first and second roll-sense axes. Transducers 112 a and 112 c can be connected so that in-phase rotations of the symmetric guided mass systems 200 a and 200 b are not detected, which provides additional rejection of externally applied angular acceleration about the X-input axis.

FIG. 4 illustrates an embodiment of a gyroscope comprising a stress relieved guided mass system 400 in accordance with the present invention. The stress relieved guided mass system 400 comprises a symmetric guided mass system 200 coupled to a stress-relief frame 402. The stress relief frame 402 is connected to the guiding arms 104 a and 104 b via springs 108 a and 108 b and surrounds the symmetric guided mass system 200. The stress relief frame 402 includes two stress relief frame members 404 a and 404 b which are coupled to the anchors 406 a and 406 b respectively via stress relief springs 408 a-d. The stress relief members 404 a and 404 b can also be flexible.

Anchors 406 a and 406 b might experience motion such as translation, expansion, or shearing as a result of thermal stress, packaging stress, or other externally applied stresses. Anchor motion can cause stress, such as tension, on the symmetric guided mass system, resulting in errors such as changing stiffness and resonant frequencies; anchor motion can also cause unwanted motion of the symmetric guided mass system resulting in errors. The stress-relief frame 402 reduces stresses and unwanted motion of the symmetric guided mass system 200.

FIG. 5 illustrates an embodiment of a dual-axis gyroscope comprising guided mass system 500 in accordance with the present invention. The guided mass system 500 comprises a guided mass system 100 coupled to a yaw proof-mass 518 a. The yaw proof-mass 518 a is flexibly connected to the roll proof-mass 102 a via yaw-springs 520 a-d. Yaw-springs 520 a-d are stiff in the X-direction such that when the guided mass system is driven, the yaw proof-mass 518 a also translates with the roll proof-mass 102 a in the X-direction.

Angular velocity about a yaw-input axis in the Z-direction will cause a Coriolis force to act on the yaw proof-mass 518 a in the Y-direction resulting in motion of the yaw proof-mass 518 a in the Y-direction. A transducer 522 a is used to sense the motion of the yaw proof-mass 518 a in the Y-direction which provides a measure of the angular velocity about the yaw-input axis.

FIG. 6 illustrates a second embodiment of a dual-axis gyroscope comprising a guided mass system 600 surrounded by a stress relief frame 402 in accordance with the present invention. The guided mass system 600 comprises a symmetric guided mass system 200 coupled to a pitch proof-mass 650 a. The stress relief frame 402 is connected to the guiding arms 104 a and 104 b via springs 108 a and 108 b and surrounds the symmetric guided mass system 200.

The pitch proof-mass 650 a is flexibly connected to the two roll proof-masses 102 a and 102 b via springs 652 a and 652 b. Springs 652 a and 652 b are torsionally compliant such that pitch proof-mass 650 a can rotate out-of-plane about a pitch sense axis in the Y-direction. Springs 652 a and 652 b are compliant in-plane such that when the roll proof-masses 102 a and 102 b are driven anti-phase in the X-direction; the pitch proof-mass 650 a rotates in-plane about an axis in the Z-direction.

Angular velocity about the pitch-input axis will cause Coriolis forces to act on the pitch proof-mass 650 a resulting in a torque that rotates the pitch proof-mass 650 a about the pitch-sense axis. The amplitude of the rotation of the pitch proof-mass 650 a is proportional to the angular velocity about the pitch-input axis. Transducers 660 a and 660 b are disposed on opposite sides along the X-direction under the pitch proof-mass 650 a and detect the rotation of the pitch proof-mass about the pitch-sense axis. This rotation provides a measure of the angular velocity about the pitch-input axis.

FIG. 7 illustrates a third embodiment of a dual-axis gyroscope comprising a guided mass system 700 in accordance with the present invention. The guided mass system 700 comprises a symmetric guided mass system 200 coupled to two yaw proof masses 518 a and 518 b. The yaw proof-masses 518 a and 518 b are flexibly connected to the roll proof-masses 102 a and 102 b via springs 520 a-d and 520 e-h respectively. When the guided mass system 700 is driven, the yaw proof-masses 518 a and 518 b also translate anti-phase in the X-direction.

Angular velocity about the yaw-input axis will cause Coriolis forces to act on the yaw proof-masses 518 a and 518 b resulting in motion of the yaw proof-masses 518 a and 518 b anti-phase along the Y-direction. The amplitude of the motion of the yaw proof-masses along the Y-direction is proportional to the angular velocity. Transducers 522 a and 522 b are used to sense the motion of the respective yaw proof masses 518 a and 518 b along the Y-direction.

FIG. 8 illustrates an embodiment of a tri-axis gyroscope comprising a guided mass system 800 surrounded by a stress relief frame 402 in accordance with the present invention. The guided mass system 800 comprises guided mass system 600 coupled to two yaw proof masses 518 a and 518 b. The stress relief frame 402 is connected to the guiding arms 104 a and 104 b via springs 108 a and 108 b and surrounds the symmetric guided mass system 200. The yaw proof-masses 518 a and 518 b are flexibly connected to the roll proof-masses 102 a and 102 b via springs 520 a-d and 520 e-h respectively. When the guided mass system 800 is driven, the yaw proof-masses 518 a and 518 b also translate anti-phase in the X-direction.

Angular velocity about the roll-input axis will cause Coriolis forces to act on the roll proof-masses 102 a and 102 b anti-phase in the Z-direction. The Coriolis forces cause the guided mass system 800 to rotate out-of-plane about the first roll-sense axis. When the guided mass system 800 rotates out-of-plane, the guiding arms 104 a and 104 b rotate about the first roll-sense axis, and the roll proof-masses 102 a and 102 b are constrained to move anti-phase out-of-plane by the guiding arms 104 a and 104 b. Transducers 112 a and 112 b under the roll proof masses 102 a and 102 b respectively are used to detect the rotation of the guided mass system 800 about the first roll-sense axis. This rotation provides a measure of the angular velocity about the roll-input axis.

Angular velocity about the pitch-input axis will cause Coriolis forces to act on the pitch proof-mass 650 a resulting in a torque that rotates the pitch proof-mass 650 a about the pitch-sense axis. The amplitude of the rotation of the pitch proof-mass 650 a is proportional to the angular velocity about the pitch-input axis. Transducers 660 a and 660 b are disposed on opposite sides along the X-direction under the pitch proof-mass 650 a and detect the rotation of the pitch proof-mass about the pitch-sense axis which provides a measure of the angular velocity about the pitch-input axis.

Angular velocity about the yaw-input axis will cause Coriolis forces to act on the yaw proof-masses 518 a and 518 b resulting in motion of the yaw proof-masses 518 a and 518 b anti-phase along the Y-direction. The amplitude of the motion of the yaw proof-masses along the Y-direction is proportional to the angular velocity. Transducers 522 a and 522 b are used to sense the motion of the respective yaw proof masses 518 a and 518 b along the Y-direction.

FIG. 9 illustrates an embodiment of a dual-axis gyroscope comprising a balanced guided mass system 900 in accordance with the present invention. The guided mass system 900 comprises two guided mass systems 600 a and 600 b coupled together by coupling spring 302 a. The guided mass systems 600 a and 600 b are connected to anchoring points 106 a-d via springs 108 a-d. In another embodiment the guided mass systems 600 a and 600 b can be coupled to the stress relief frame 402 via springs 108 a-d.

The symmetric guided mass system 600 a rotates out-of-plane about a first roll-sense axis. The symmetric guided mass system 600 b rotates out-of-plane about a second roll-sense axis in-plane and parallel to the first roll-sense axis. The coupling spring 302 a is connected to roll proof-masses 102 b and 102 c. The coupling spring 302 a is torsionally compliant about an axis in the X-direction so that the symmetric guided mass systems 600 a and 600 b can rotate anti-phase out-of-plane about the first and second roll-sense axes. The coupling spring 302 a is stiff in the Z-direction which prevents the symmetric guided mass systems 600 a and 600 b from rotating in-phase out-of-plane. Pitch proof-masses 650 a and 650 b are each flexibly connected to their respective four roll proof-masses 102 a-102 d via springs 652 a-d. Springs 652 a and 652 b are torsionally compliant such that pitch proof-mass 650 a can rotate out-of-plane about a first pitch sense axis in the Y-direction, and springs 652 c and 652 d are torsionally compliant such that pitch proof-mass 650 b can rotate out-of-plane about a second pitch sense axis in the Y-direction.

The two symmetric guided mass systems 600 a and 600 b are arranged so that the roll proof-masses 102 a-d all move in the X-direction. The coupling spring 302 a is stiff in the X-direction such that roll proof-masses 102 b and 102 c move together in the X-direction. The roll proof-masses 102 a and 102 d move in opposite of roll proof-masses 102 b and 102 c. Springs 652 a-d are compliant in-plane such that when the roll proof-masses 102 a-d are driven, the pitch proof-masses 650 a and 650 b rotate anti-phase in-plane about separate axes in the Z-direction. Electrostatic actuators 109 a-h such as comb drives, are connected to the roll proof-masses 102 a-d to drive the balanced guided mass system 900. The two guided mass systems 600 a and 600 b comprising roll proof-masses 102 a-d and pitch proof-masses 650 a and 650 b are driven together at a drive frequency by a single drive circuit coupled to the actuators 109 a-h.

Angular velocity about the pitch-input axis in the X-direction will cause Coriolis forces to act on the pitch proof-masses 650 a and 650 b about the first and second pitch-sense axes respectively. The Coriolis forces cause the pitch proof masses 650 a and 650 b to rotate anti-phase out-of-plane about the first and the second pitch-sense axes. The amplitudes of the rotations of the pitch proof-masses 650 a and 650 b about the first and the second pitch-sense axes are proportional to the angular velocity about the pitch-input axis. Transducers 660 a-660 d under the pitch proof masses 650 a and 650 b are used to detect the anti-phase rotations about the first and the second pitch-sense axes. Externally applied angular acceleration about the pitch-input axis will generate inertial torques in-phase on the pitch proof masses 650 a and 650 b causing them to rotate in-phase about the first and the second pitch-sense axes. Transducers 660 a and 660 d can be coupled and transducers 660 b and 660 c can be coupled so that in-phase rotations of the pitch proof-masses 650 a and 650 b are not detected, but anti-phase rotations are detected.

Angular velocity about the roll-input axis will cause Coriolis forces to act on the roll proof-masses 102 a-d in the Z-direction. The Coriolis forces cause the symmetric guided mass systems 600 a and 600 b to rotate anti-phase out-of-plane about the first and second roll-sense axes. Transducers 112 a-c under the roll proof masses 102 a-d are used to detect the rotations of the symmetric guided mass systems 600 a and 600 b. Externally applied angular acceleration about the pitch-input axis will generate in-phase inertial torques on the symmetric guided mass systems 600 a and 600 b. However, the symmetric guided mass systems 600 a and 600 b do not rotate because coupling spring 302 a prevents in-phase rotation about the first and second roll-sense axes. Transducers 112 a and 112 c can be coupled so that in-phase rotations of the symmetric guided mass systems 600 a and 600 b are not detected but anti-phase rotations are detected.

FIG. 10 illustrates another embodiment of a dual-axis gyroscope comprising a balanced guided mass system 1000 in accordance with an embodiment of the present invention. The guided mass system 1000 includes two symmetric guided mass systems 700 a and 700 b which are connected by a coupling spring 302 a.

The two symmetric guided mass systems 700 a and 700 b are arranged so that the roll proof-masses 102 a-d all move in the X-direction. The symmetric guided mass system 700 a rotates out-of-plane about a first roll-sense axis. The symmetric guided mass system 700 b rotates out-of-plane about a second roll-sense axis in-plane and parallel to the first roll-sense axis. The coupling spring 302 a is connected to roll proof-masses 102 b and 102 c. The coupling spring 302 a is stiff in the X-direction such that roll proof-mass 102 b and 102 c move together in the X-direction. In this way the two guided mass systems 700 a and 700 b are driven together at a drive frequency by a single drive circuit coupled to the actuators 109 a-h. The coupling spring 302 a is torsionally compliant about an axis in the X-direction so that the symmetric guided mass systems 700 a and 700 b can rotate anti-phase out-of-plane about the first and second roll-sense axes. The coupling spring 302 a is stiff in the Z-direction which prevents the symmetric guided mass systems 700 a and 700 b from rotating in-phase out-of-plane.

Angular velocity about the yaw-input axis will cause Coriolis forces to act on the yaw proof-masses 518 a-d resulting in motion of the yaw proof-masses 518 a-d along the Y-direction. The amplitude of the motions of the yaw proof-masses 518 a-d is proportional to the angular velocity about the yaw-input axis. Transducers 522 a-d are used to sense the motion of the respective yaw proof masses 518 a-d in the Y-direction.

Angular velocity about the roll-input axis will cause Coriolis forces to act on the roll proof-masses 102 a-d in the Z-direction. The Coriolis forces cause the symmetric guided mass systems 700 a and 700 b to rotate anti-phase out-of-plane about the first and second roll-sense axes. The amplitudes of the rotations of the symmetric guided mass systems 700 a and 700 b are proportional to the angular velocity. Transducers 112 a-c under the roll proof masses 102 a-d are used to detect the rotations of the symmetric guided mass systems 700 a and 700 b. Externally applied angular acceleration about the pitch-input axis will generate in-phase inertial torques on the symmetric guided mass systems 700 a and 700 b. However, the symmetric guided mass systems 700 a and 700 b do not rotate because coupling spring 302 a prevents in-phase rotation about the first and second roll-sense axes. Transducers 112 a and 112 c can be coupled so that in-phase rotations of the symmetric guided mass systems 700 a and 700 b are not detected but anti-phase rotations are detected.

FIG. 11 illustrates an embodiment of a tri-axis gyroscope comprising a multiple guided mass system 1100 in accordance with the present invention. The multiple guided mass system 1100 includes two guided mass systems 500 a and 500 b coupled to a guided mass system 600 by coupling springs 302 a and 302 b.

The guided mass systems 500 a, 500 b and 600 are arranged so that the roll proof-masses 102 a-d all move in the X-direction, the pitch proof-mass 650 a rotates about an axis in the Z-direction, and the yaw proof-masses 518 a and 518 b move anti-phase in the X-direction. The guided mass system 500 a rotates out-of-plane about a first roll-sense axis. The symmetric guided mass system 600 rotates out-of-plane about a second roll-sense axis parallel to the first roll-sense axis. The guided mass system 500 b rotates out-of-plane about a third roll-sense axis parallel to the first and second roll-sense axes. The first coupling spring 302 a is connected to roll proof-masses 102 a and 102 b. The coupling spring 302 a is stiff in the X-direction such that roll proof-mass 102 a and 102 b move together in the X-direction. The second coupling spring 302 b is connected to roll proof-masses 102 c and 102 d. The coupling spring 302 b is stiff in the X-direction such that roll proof-mass 102 c and 102 d move together in the X-direction. In this way the guided mass systems 500 a, 500 b, and 600 are driven together at a drive frequency by a single drive circuit coupled to the actuators 109 a-h.

The coupling spring 302 a is torsionally compliant about an axis in the X-direction so that the guided mass systems 500 a and 600 can rotate out-of-plane about the first and second roll-sense axes anti-phase. The coupling spring 302 a prevents the symmetric guided mass systems 500 a and 600 from rotating out-of-plane in-phase.

The coupling spring 302 b is also torsionally compliant about an axis in the X-direction so that the guided mass systems 500 b and 600 can rotate out-of-plane about the second and third roll-sense axes anti-phase. The coupling spring 302 b prevents the symmetric guided mass systems 500 b and 600 from rotating out-of-plane in-phase.

Angular velocity about the pitch-input axis will cause Coriolis forces to act on the pitch proof-mass 650 a resulting in a torque that rotates the pitch proof-mass 650 a about the pitch-sense axis. The amplitude of the rotation of the pitch proof-mass 650 a is proportional to the angular velocity about the pitch-input axis. Transducers 660 a and 660 b are disposed on opposite sides along the X-direction under the pitch proof-mass 650 a and detect the rotation of the pitch proof-mass about the pitch-sense axis. The rotation provides a measure of the angular velocity about the pitch-input axis.

Angular velocity about the roll-input axis will cause Coriolis forces to act on the roll proof-masses 102 a and 102 b in a Z-direction and on roll proof-masses 102 c and 102 d in the opposite Z-direction. The Coriolis forces cause the guided mass systems 500 a, 600, and 500 b to rotate out-of-plane about the first, second, and third roll-sense axis respectively. Transducer 112 a under the roll proof masses 102 a and 102 b and transducer 112 b under the roll proof masses 102 c and 102 d are used to detect the rotation of the guided mass system 1100. This rotation provides a measure of the angular velocity about the roll-input axis.

Angular velocity about the yaw-input axis will cause Coriolis forces to act on the yaw proof-masses 518 a and 518 b resulting in motion of the yaw proof-masses 518 a and 518 b anti-phase along the Y-direction. The amplitude of the motion of the yaw proof-masses along the Y-direction is proportional to the angular velocity. Transducers 522 a and 522 b are used to sense the motion of the respective yaw proof masses 518 a and 518 b along the Y-direction.

FIG. 12A illustrates an embodiment of a tri-axis gyroscope comprising a multiple guided mass system 1200 in accordance with the present invention. The multiple guided mass system 1200 comprises the multiple guided mass system 1100 coupled to a stress relief frame 402.

The stress relief frame 402 is connected to the guiding arms 104 a-f via springs 108 a-f respectively and surrounds the multiple guided mass system 1100.

The guided mass systems 500 a, 500 b and 600 are arranged so that when the roll proof-masses 102 a-d all move in the X-direction, the pitch proof-mass 650 a rotates about an axis in the Z-direction, and the yaw proof-masses 518 a and 518 b move anti-phase in the X-direction, as shown in FIG. 12B. The guided mass systems 500 a, 500 b, and 600 are driven together at a drive frequency by a single drive circuit coupled to the actuators 109 a-h.

Angular velocity about the pitch-input axis will cause Coriolis forces to act on the pitch proof-mass 650 a resulting in a torque that rotates the pitch proof-mass 650 a about the pitch-sense axis, as shown in FIG. 12C. The amplitude of the rotation of the pitch proof-mass 650 a is proportional to the angular velocity about the pitch-input axis. Transducers 660 a and 660 b are disposed on opposite sides along the X-direction under the pitch proof-mass 650 a and detect the rotation of the pitch proof-mass about the pitch-sense axis. The rotation provides a measure of the angular velocity about the pitch-input axis.

Angular velocity about the roll-input axis will cause Coriolis forces to act on the roll proof-masses 102 a and 102 b in a Z-direction and on roll proof-masses 102 c and 102 d in the opposite Z-direction. The Coriolis forces cause the guided mass systems 500 a, 600, and 500 b to rotate out-of-plane about the first, second, and third roll-sense axis respectively, as shown in FIG. 12D. Transducer 112 a under the roll proof masses 102 a and 102 b and transducer 112 b under the roll proof masses 102 c and 102 d are used to detect the rotation of the guided mass system 1100. This rotation provides a measure of the angular velocity about the roll-input axis.

Angular velocity about the yaw-input axis will cause Coriolis forces to act on the yaw proof-masses 518 a and 518 b resulting in motion of the yaw proof-masses 518 a and 518 b anti-phase along the Y-direction, as shown in FIG. 12E. The amplitude of the motion of the yaw proof-masses along the Y-direction is proportional to the angular velocity. Transducers 522 a and 522 b are used to sense the motion of the respective yaw proof masses 518 a and 518 b along the Y-direction.

CONCLUSION

A gyroscope in accordance with the present invention includes one or more guided mass systems that oscillates at one frequency and is capable of sensing angular rate about multiple axes. In a preferred embodiment, one drive motion requires only one drive circuit, which lowers cost and power. Although the present invention has been described in accordance with the embodiments shown, one of ordinary skill in the art will readily recognize that there could be variations to the embodiments and those variations would be within the spirit and scope of the present invention. Accordingly, many modifications may be made by one of ordinary skill in the art without departing from the spirit and scope of the appended claims. 

What is claimed is:
 1. A gyroscope comprising; a substrate; a guided mass system, the guided mass system comprising at least one proof-mass and at least one guiding arm; wherein the proof-mass and the guiding arm are disposed in a plane parallel to the substrate; the at least one proof-mass being coupled to the at least one guiding arm; the at least one guiding arm being coupled to the substrate through a coupling comprising at least one flexible member; wherein the proof-mass vibrates in a first direction in the plane and the guiding arm rotates in the plane; wherein in response to angular velocity about a first input axis, an end of the guiding arm is able to rotate out of the plane and the proof-mass is able to rotate out of the plane; an actuator for rotating the guiding arm in the plane; and a transducer for generating an output in response to the angular velocity of the at least one proof-mass.
 2. The gyroscope of claim 1, wherein the transducer comprises a capacitive transducer.
 3. The gyroscope of claim 1, wherein the angular velocity generates a Coriolis force on the at least one proof mass.
 4. The gyroscope of claim 1, wherein actuator comprises an electrostatic actuator, wherein the electrostatic actuator includes a fixed comb and a moving comb, wherein the moving comb is disposed in the plane and the fixed comb is coupled to an anchor.
 5. The gyroscope of claim 1, wherein the at least one guiding arm comprises two guiding arms.
 6. The gyroscope of claim 1 wherein the at least one proof-mass comprises at least two proof masses, the at least two proof-masses being coupled to at least one guiding arm, the at least one guiding arm being coupled to the substrate through at least one flexible member; wherein the two proof masses move in anti-phase along the first direction; wherein the at least one guiding arm and the two proof-masses are able to rotate out of the plane in response to angular velocity about the first input axis that is in the plane.
 7. The gyroscope of claim 1 further comprising: at least one other proof mass coupled to the at least one proof mass, wherein when the at least one proof mass is vibrating the at least one other proof mass vibrates; and at least one other transducer for sensing motion of the at least one other proof-mass in response to angular velocity about an axis other than the first input axis.
 8. The A gyroscope comprising; a substrate; a guided mass system, the guided mass system comprising at least one proof-mass and at least one guiding arm; the at least one proof-mass being coupled to the at least one guiding arm; the at least one guiding arm being coupled to the substrate through at least one flexible member; wherein the proof-mass vibrates in a first direction and the guiding arm rotates; wherein the at least one guiding arm and the at least one proof-mass are able to rotate about a first sense axis in response to angular velocity about a first input axis; an actuator for vibrating the at least one proof-mass in the first direction; a transducer for generating an output in response to the angular velocity of the at least one proof-mass; wherein the at least one proof-mass comprises at least two proof masses, the at least two proof-masses being coupled to at least one guiding arm, the at least one guiding arm being coupled to the substrate through at least one flexible member; wherein the two proof masses move in anti-phase along the first direction; wherein the at least one guiding arm and the two proof-masses are able to rotate out of a plane about the first sense axis in response to angular velocity about the first input axis that is in the plane; at least one other proof-mass coupled to the at least one proof mass, wherein when the at least one proof mass is vibrating the at least one other proof-mass rotates in plane; and a second transducer for detecting the rotation of the at least one other proof-mass about a second sense axis orthogonal to the first sense axis responding to angular velocity about a second input axis that is in plane and orthogonal to the first input axis.
 9. The A gyroscope comprising: a substrate; a guided mass system, the guided mass system comprising at least one proof-mass and at least one guiding arm; the at least one proof-mass being coupled to the at least one guiding arm; the at least one guiding arm being coupled to the substrate through at least one flexible member; wherein the proof-mass vibrates in a first direction and the guiding arm rotates; wherein the at least one guiding arm and the at least one proof-mass are able to rotate about a first sense axis in response to angular velocity about a first input axis; an actuator for vibrating the at least one proof-mass in the first direction; a transducer for generating an output in response to the angular velocity of the at least one proof-mass; at least one other proof-mass coupled to the at least one proof mass, wherein when the at least one proof mass vibrates, the at least one other proof-mass translates in the first direction and in response to angular rotation of the gyroscope about a second input axis normal to the plane, the at least one other proof-mass translates in the plane orthogonal to the first direction; and a second transducer for detecting motion of the at least one other proof-mass in the plane orthogonal to the first direction.
 10. A gyroscope comprising; a substrate; a guided mass system, the guided mass system comprising a first proof-mass and at least one guiding arm; the first proof-mass being coupled to the at least one guiding arm; the at least one guiding arm being coupled to the substrate through at least flexible member; wherein the at least one guiding arm allows for motion of the first proof-mass in a first direction; wherein the at least one guiding arm and the first proof-mass are able to rotate about a first sense axis, a second proof-mass coupled to the first proof mass, wherein when first proof mass moves in the first direction, the second proof-mass rotates; a third proof-mass coupled to the first proof mass, wherein when the first proof mass moves in the first direction, the third proof-mass moves in the first direction; an actuator for vibrating the first proof-mass in the first direction; a first transducer for sensing motion of the first proof-mass normal to the plane in response to angular velocity about a first input axis; a second transducer for detecting the rotation of the second proof-mass about a second sense axis orthogonal to the first sense axis responding to angular velocity about a second input axis; and a third transducer for detecting motion of the third proof-mass in-plane and orthogonal to the first direction in response to angular rotation of the gyroscope about a third input axis.
 11. The gyroscope of claim 10 further comprising: a stress relief frame, wherein the at least one guiding arm is flexibly coupled to the stress relief frame via the at least one flexible member, wherein the stress relief frame is coupled to the substrate, wherein the stress relief frame decouples motion of the substrate coupling points from the at least one flexible member.
 12. A gyroscope comprising: a substrate; a first guided mass system, the first guided mass system comprising at least one proof-mass and at least one guiding arm; the at least one proof-mass being coupled to the at least one guiding arm; the at least one guiding arm being coupled to the substrate through at least one flexible member; wherein the at least one proof-mass vibrates and the guiding arm rotates in a plane parallel to the substrate; wherein the at least one guiding arm and the at least one proof-mass rotate out of the plane in response to angular velocity about a first input axis; a first spring; a second guided mass system, the second guided mass system coupled by the first spring to the first guided mass system; the second guided mass system comprising at least one second proof-mass and at least one second guiding arm; the at least one second proof-mass being coupled to the at least one second guiding arm; the at least one second guiding arm being coupled to the substrate through at least one second flexible member; wherein the second proof-mass vibrates in a first direction and the guiding arm rotates in the plane; wherein the at least one second guiding arm and the at least one second proof-mass rotate out of the plane in response to angular velocity about the first input axis; wherein the at least one proof-mass rotates about a first axis in response to angular rate, the second proof-mass rotates about a second axis in response to angular rate, and the at least one proof-mass and the second proof-mass rotate in anti-phase in response to angular rate; an actuator for vibrating the second proof-mass in the first direction; and a transducer for sensing motion of the at least one proof-mass in response to angular velocity.
 13. The gyroscope of claim 12 further comprising: a stress relief frame, wherein the at least one guiding arm is flexibly coupled to the stress relief frame via the at least one flexible members of the first and second guided mass systems, wherein the stress relief frame is coupled to the substrate; wherein the stress relief frame decouples motion of the substrate coupling points from the at least one spring to prevent stress on the at least one flexible member.
 14. The gyroscope of claim 12 further comprising: a second spring; a third guided mass system, the third guided mass system coupled by the second spring to the first guided mass system; the third guided mass system comprising at least a third proof-mass and at least a third guiding arm; the third proof-mass being coupled to the third guiding arm; the third guiding arm being coupled to the substrate through at least one third flexible member; wherein the third guiding arm allows for motion of the third proof-mass in the first direction; wherein the third guiding arm and the third proof-mass rotate out of the plane, wherein the second proof mass rotates out of the plane in response to angular rate, the third guided mass system rotates out of the plane in response to angular rate, and the second and third guided mass systems rotate anti-phase in response to angular rate.
 15. The gyroscope of claim 14 further comprising: a stress relief frame, wherein the at least one guiding arm is flexibly coupled to the stress relief frame via one or more of the at least one flexible member of the first, second and third guided mass systems, wherein the stress relief frame is coupled to the substrate, wherein the stress relief frame decouples motion of the substrate coupling points from the at least one flexible member.
 16. A gyroscope comprising; a substrate; a guided mass system, the guided mass system comprising at least two proof-masses and at least one guiding arm; the at least two proof-masses being coupled to the at least one guiding arm; the at least one guiding arm being coupled to the substrate through at least flexible member; wherein the at least one guiding arm allows for anti-phase motion of the at least two proof-masses; at least one other proof-mass coupled to the at least two proof masses, wherein when the at least two proof masses move anti-phase in the first direction the at least one other proof-mass rotates; and an actuator for vibrating the at least two proof-masses antiphase in the first direction; and a transducer for detecting the rotation of the at least one other proof-mass about a sense axis responding to angular velocity.
 17. A gyroscope comprising; a substrate; a guided mass system, the guided mass system comprising at least one proof-mass and at least one guiding arm; wherein the proof-mass and the guiding arm are disposed in a plane parallel to the substrate; the at least one proof-mass being coupled to the at least one guiding arm; the at least one guiding arm being coupled to the substrate through a coupling comprising at least one flexible member; wherein the proof-mass vibrates in a first direction in the plane and the guiding arm rotates in the plane; wherein in response to angular velocity about a first input axis, a first end portion of the guiding arm is able to rotate out of the plane and the proof-mass is able to rotate out of the plane.
 18. The gyroscope of claim 17, wherein a first end portion of the guiding arm is able to rotate out of the plane about a first rotation axis; and the proof-mass is able to rotate out of the plane about a second rotation axis.
 19. The gyroscope of claim 18, wherein the first rotation axis and the second rotation axis are not coincident.
 20. The gyroscope of claim 18, wherein the angle between the first rotation axis and the first direction is less than 45 degrees.
 21. The gyroscope of claim 17, wherein the first end portion of the guiding arm is coupled to the proof-mass; the guiding arm further comprises a second end portion; the second end portion of the guiding arm is coupled to the substrate through the coupling comprising the at least one flexible member; and the guiding arm is configured so that the first end portion rotates further out of the plane than the second end portion in response to angular velocity about a first input axis.
 22. The gyroscope of claim 17, wherein the coupling comprises a direct connection between the substrate and the guide arm via one flexible member and an anchoring point.
 23. The gyroscope of claim 17, wherein the flexible member is elongated in a direction parallel to the first direction.
 24. The gyroscope of claim 23, wherein the flexible member is doubly folded.
 25. A gyroscope comprising; a substrate; a guided mass system, the guided mass system comprising at least one proof-mass and at least one guiding arm; wherein the proof-mass and the guiding arm are disposed in a plane parallel to the substrate; the at least one proof-mass being coupled to a first end portion of the at least one guiding arm; a second end portion of the at least one guiding arm being coupled to the substrate through a coupling comprising at least one flexible member; wherein the proof-mass vibrates in a first direction in the plane and the guiding arm rotates in the plane; wherein in response to angular velocity about a first input axis, the first end portion of the guiding arm is able to rotate out of the plane and the proof-mass is able to rotate out of the plane; and wherein the guiding arm is configured so that the first end portion rotates further out of the plane than the second end portion in response to angular velocity about a first input axis.
 26. The gyroscope of claim 25, wherein a first end portion of the guiding arm is able to rotate out of the plane about a first rotation axis; and the proof-mass is able to rotate out of the plane about a second rotation axis.
 27. The gyroscope of claim 26, wherein the first rotation axis and the second rotation axis are not coincident.
 28. A gyroscope comprising; a substrate; a guided mass system, the guided mass system comprising at least one proof-mass and at least one guiding arm; wherein the proof-mass and the guiding arm are disposed in a plane parallel to the substrate; the at least one proof-mass being coupled to the at least one guiding arm; the at least one guiding arm being coupled to the substrate through a coupling comprising a direct connection between the substrate and the guide arm via one flexible member and an anchoring point; wherein the proof-mass vibrates in a first direction in the plane and the guiding arm rotates in the plane; wherein in response to angular velocity about a first input axis, a first end portion of the guiding arm is able to rotate out of the plane and the proof-mass is able to rotate out of the plane.
 29. The gyroscope of claim 28, wherein a first end portion of the guiding arm is able to rotate out of the plane about a first rotation axis; and the proof-mass is able to rotate out of the plane about a second rotation axis.
 30. The gyroscope of claim 29, wherein the first rotation axis and the second rotation axis are not coincident.
 31. The gyroscope of claim 28, wherein the first end portion of the guiding arm is coupled to the proof-mass; the guiding arm further comprises a second end portion; the second end portion of the guiding arm is coupled to the substrate through the coupling comprising the at least one flexible member; and the guiding arm is configured so that the first end portion rotates further out of the plane than the second end portion in response to angular velocity about a first input axis.
 32. The gyroscope of claim 28, further comprising an actuator configured to oscillate the at least one proof-mass in the first direction; and a transducer for generating an output in response to the angular velocity of the at least one proof-mass.
 33. The gyroscope of claim 28, wherein the flexible member is doubly folded.
 34. A method of responding to angular velocity about an input axis, comprising: oscillating an actuator suspended on an actuator mass in a plane parallel to a substrate, wherein the actuator mass oscillates along a first axis in the plane; rotating a suspended guiding arm that is anchored to the substrate via a flexible element and an anchoring point, wherein the guiding arm is disposed in the plane and the rotating occurs in the plane, wherein the guiding arm has a first end portion that is coupled to a suspended proof-mass via at least a first spring and a second end portion that is coupled to the actuator mass via at least a second spring, wherein the oscillation of the actuator is transmitted via the second spring and causes the rotating; oscillating the proof-mass along a second axis in the plane, wherein the rotating of the guiding arm is transmitted via the first spring and causes the oscillating of the proof-mass; in response to an angular velocity about an input axis that is orthogonal to the first direction, rotating the first end portion of the guiding arm out of plane and rotating the proof mass out of plane; detecting, with a transducer, the motion of the proof-mass normal to the plane; and generating an output with the transducer based upon the amplitude of the rotation of the proof mass out of the plane.
 35. The method of claim 34, wherein the first axis is not coincident with the second axis.
 36. A gyroscope comprising, a substrate an actuator arm suspended in a plane parallel to the substrate; an actuator attached to the actuator arm, wherein the actuator is a comb drive; a guiding arm suspended in the plane, the guiding arm having a first end portion and a second end portion; a first spring coupling the actuator arm to the first end portion of the guiding arm; a proof mass; a second spring coupling the proof mass to the second end portion of the guiding arm; wherein the actuator is configured to oscillate the actuator arm along an actuation axis in the plane; wherein oscillation of the actuator arm will cause the guiding arm to rotate in the plane; wherein the rotation of the guiding arm in the plane will cause the proof mass to oscillate along an oscillation axis; wherein the oscillation axis is not coincident with the actuation axis; and wherein in response to angular velocity about an input axis, the second end portion of the guiding arm is able to rotate out of the plane and the proof-mass is able to rotate out of the plane.
 37. The gyroscope of claim 36, wherein, the width of the first end portion measured in the plane is greater than the width of the first spring at the connection of the first end portion to the first spring; and the width of the second end portion measured in the plane is greater than the width of the second spring at the connection of the second end portion to the second spring.
 38. The gyroscope of claim 36, wherein the guiding arm comprises an L-shaped portion.
 39. The gyroscope of claim 38, wherein the first end portion is offset from the second end portion at a right angle within the plane. 